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- Manufacturer
- Bombardier
- Type
- Service Bulletin
- Number
- 604-28-022
- Latest revision known
- 604-28-022, Revision 3, dated August 31, 2018
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- 2 files of 2 revisions
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Discard the Revision 02 of this Service Bulletin dated May 14, 2018 and replace in its entirety with this Revision 03.
Service Bulletin No. 604−28−022 Date of Basic Issue Oct 19/2015 Revision No. 01 Dated Nov 03/2017 Revision No. 02 Dated May 14/2018 Revision No. 03 Dated Aug 31/2018 This Service Bulletin contain special check instructions and must be repeated every 600 flight hours or 12 months, whichever comes first.
This revision is issued to update the instructions applicable for this Service Bulletin. The changes are as follows:
1. Add Retroactive action.
2. Change in Paragraph 1.K., to update the new revision of the Restriction and/or Special Instruction (RSI), C−4127, Rev. F.
3. Change in Paragraph 2.A.(4), to clarify the refuel step.
4. Make miscellaneous minor changes, as necessary, with no change of context.
SERVICE BULLETIN MODEL CL−600−2B16 604−28−022 Page 1 of 1
REVISION TRANSMITTAL SHEET
SPECIAL CHECK - STANDBY FUEL FEED SYSTEM AND AUXILIARY POWER UNIT (APU) FUEL FEED SYSTEM - ENGINE AND APU ELECTRICAL FUEL PUMP
CARTRIDGE/CANISTER FUEL LEAKAGE The information below is provided for your reference. For full details, including labor and part coverage, please see corresponding paragraph contained within this bulletin.
RECOMMENDED
SPECIFIED TIME COMPLIANCE
COMPLIANCE TIME Refer to Paragraph 1.D.
EFFECTIVITY: A/C Serial No. 5301 to 5665 MANPOWER: 5 man−hours
CONTINUED AIRWORTHINESS (CAW)
FLEET CAMPAIGN NOYES TLMC, CH 5 AFFECTED NOYES KITS and/or PARTS YES NO
TOOLING/GSE NOYES PLANNING INFORMATION: See important information at the start of Paragraph 1. YES NO
DEDICATED SCHEDULE NOYES PREREQUISITE SERVICE BULLETINS: N/A To place an order for parts or kits, please call Bombardier Aerospace Parts Services at:
514−855−2999 or 1−866−538−1247
SERVICE BULLETIN SUMMARY my.businessaircraft.bombardier.com MODEL CL−600−2B16 ATA 28−23, 28−24 FUEL Basic Issue: Oct 19/2015 Revision 03: Aug 31/2018 604−28−022 Page 1 of 1 This Service Bulletin is available at:
SPECIAL CHECK - STANDBY FUEL FEED SYSTEM AND AUXILIARY POWER UNIT (APU) FUEL FEED SYSTEM - ENGINE AND APU ELECTRICAL FUEL PUMP
CARTRIDGE/CANISTER FUEL LEAKAGE
RETROACTIVE ACTION
THE ACTION THAT FOLLOWS IS RECOMMENDED FOR AIRCRAFT ON WHICH THE BASIC ISSUE OF THIS SERVICE BULLETIN WAS DONE:
Perform the Revision 03 of this Service Bulletin within 4 months or 150 Flight Hours from Service Bulletin release date Revision 03 or 12 months from the last inspection of the Basic Issue. Whichever comes first.
And continue the repetitive inspections of this Service Bulletin (Revision 03) per the Compliance in PARA 1.D.
NO RETROACTIVE ACTION IS REQUIRED FOR AIRCRAFT ON WHICH THE REVISION 01 OR REVISION 02 OF THIS SERVICE BULLETIN WAS DONE.
1. PLANNING INFORMATION NOTES:1 . Before you do this bulletin, examine all STC, STA or equivalent action changes to make sure that this bulletin can be completed.
2. In order to incorporate this Service Bulletin, you must order the following O−rings: Part No’s MS29513−034, MS29513−118 and MS29513−142 (for cartridge Part No. 226114−3). And Part No’s M25988/3−034, M25988/3−118 and M25988/3−142 (for cartridge Part No. P99C25−603).
Refer to Paragraph 3.B.
3. Make sure to complete and submit Appendix 1.
SERVICE BULLETIN my.businessaircraft.bombardier.com MODEL CL−600−2B16 ATA 28−23, 28−24 FUEL Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations and/or acceptable industry standards.
This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior written consent of Bombardier Inc. and/or its affiliates.
2015−2018 Bombardier Inc. All rights reserved Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries.
Basic Issue: Oct 19/2015 Revision 03: Aug 31/2018 604−28−022 Page 1 of 11 This Service Bulletin is available at:
A. Effectivity CL−600−2B16 aircraft, Serial No. 5301 to 5665.
NOTE: The instructions given in this Service Bulletin are only applicable to the systems and parts installed at the time of delivery of the aircraft or as changed by Bombardier Aerospace Service Bulletin(s).
B. Reason There have been reported fuel leaks in engine and APU electrical fuel pump cartridge/canister electrical connectors and conduits.
This Service Bulletin gives instructions to verify if there is any fuel leakage at the RHS landing lights compartment from the APU electrical fuel pump conduit outlet, and at FS 412.00, BL 0.0 from the RHS and LHS engine electrical fuel pump.
C. Description This Service Bulletin gives instructions to:
− Do an inspection for any possible fuel leak from LHS or RHS electrical engine pumps at the location of the one belly fairing screw, FS 412, BL 0.0 (approx.).
− Do an inspection for any possible fuel leak in the right landing lights compartment from the APU electrical fuel pump conduit outlet, − Remove the applicable boost pump cartridge to inspect and replace the three o−rings, − Do the necessary testing to make sure that there are no fuel leaks and that the system operates correctly, and − If there are any fuel leaks, contact Bombardier Aerospace Service Engineering for further instructions by submitting a Service Request for Product Support Action (SRPSA) by e−mail at: SRPSA@aero.bombardier.com.
D. Compliance Recommended within 600 flight hours or 12 months, whichever comes first from the Service Bulletin release date (Revision 01).
The inspection, must be repeated every 600 flight hours or 12 months, whichever comes first.
NOTE: If it is not possible to complete all the instructions in this Service Bulletin because of the configuration of the aircraft, submit an SRPSA for analysis and to get an approved disposition to complete this Service Bulletin.
MODEL CL−600−2B16 Basic Issue: Oct 19/2015 Revision 03: Aug 31/2018 604−28−022 Page 2 of 11
E. Approval The technical content of this Service Bulletin has been approved under the authority of Transport Canada Civil Aviation (TCCA) Design Approval Organization (DAO) No. DAO #93−Q−02.
NOTES: 1. The technical content of this Service Bulletin is accepted by the FAA under the Canada/USA bilateral Aviation Safety Agreement.
2. The technical content of this Service Bulletin is accepted by EASA under the Canada/EU bilateral Aviation Safety Agreement.
F. Manpower NOTES: 1. The man−hours given are estimates to help you schedule the tasks given in this bulletin. The estimates are for direct labor performed by an experienced crew and do not include the time for familiarization, planning, aircraft preparation in hangar such as towing and positioning of scaffolds, removal of interior furnishings, repainting, supervision and inspection.
For more information related to the manpower estimates, refer to SB604−00−002.
2. This Service Bulletin may require consumable materials that have specific curing times (refer to Paragraph 3). The accumulated curing time is not included in the man−hours and should be considered for planning purposes before you schedule this Service Bulletin.
5 man−hours is necessary to do this special check.
Bombardier Aerospace does not pay for the labor to do this special check and the repetitive special check.
G. Material − Cost and Availability No kit is necessary to do this Special Check.
The parts listed in Paragraph 3.B are necessary to replace the O−rings for the special check.
The parts required to do the Special Check and the repetitive Special Check are not covered by Bombardier.
For those aircraft out of new aircraft warranty at the time of Service Bulletin distribution, Smart Parts Plus pays for the parts for up to one year from the Service Bulletin distribution date (Revision 01).
H. Tooling No equipment or special tools are necessary.
MODEL CL−600−2B16 Basic Issue: Oct 19/2015 Revision 03: Aug 31/2018 604−28−022 Page 3 of 11
I. Weight and Balance No change.
J. Electrical Load Data No change.
K. References − Bombardier Aerospace, Restriction and/or Special Instruction (RSI), C−4127, Rev. F.
− CL−604 Aircraft Maintenance Manual (AMM), Chapters 6, 24, 28, 51 and 53.
− CL−604 Aircraft Illustrated Parts Catalog (AIPC), Chapters 20 and 51.
− Bombardier Aerospace, Standard Practices Manual (SPM), Chapter 20.
− Appendix 1 − Information Feedback Sheet. (attached) L. Other Publications Affected None.
M. Equivalent Service Bulletins For the Challenger 605 aircraft, use SB 605−28−010.
For the Challenger 650 aircraft, use SB 650−28−001.
2. ACCOMPLISHMENT INSTRUCTIONS NOTES: 1. All TASKs given in the procedures that follow are from the CL−604 Aircraft Maintenance Manual (AMM) unless otherwise specified.
2. All references made to zones, access panels and/or doors, are from the CL−604 AMM, Chapter 6.
A. Aircraft Setup NOTE: The steps in the Aircraft Set−Up section of this Service Bulletin are recommended steps. The steps give a recommendation to get access to the work area. This recommendation is to give a safe work area and to minimize possible damage to surrounding aircraft parts. Alternative steps can be used at the operator discretion.
(1) Obey all electrical/electronic safety precautions. Refer to AMM 24−00−00−910−801.
(2) Obey the fuel system safety precautions. Refer to AMM 28−00−00−910−801.
(3) Remove one belly fairing screw located at FS412.00, BL0.0 (approximately).
Keep the screw to re−install later. Refer to Figure 1.
(4) Refuel the LH, RH and Auxiliary tank to a minimum of 3,200 lbs in each tank.
MODEL CL−600−2B16 Basic Issue: Oct 19/2015 Revision 03: Aug 31/2018 604−28−022 Page 4 of 11
B. Special Check− Inspection of the Engines and APU Electric Fuel Pump Cartridges/Canisters conduit area without removing the fairing NOTE: If it is not possible to complete all the instructions in this Service Bulletin because of the configuration of the aircraft, submit an SRPSA for analysis and to get an approved disposition to complete this Service Bulletin.
(1) Inspect the canister connector cavities and wiring conduits for fuel leakage as per the steps that follow:
NOTE: The applicable fuel tank (Auxiliary tank for the RH and LH engine electric fuel pumps and RH wing tank for APU electric fuel pump) must contain a minimum of 3200 lbs. of fuel for the steps that follow.
(a) Please use Appendix 1 of this Service Bulletin to record your data from this Special Inspection and send it via email:
BAG_BBAD_CL600_Program@aero.bombardier.com
(b) Install the wheel chocks at the nose and main landing gear wheels.
(c) Remove the RHS, LHS and APU fuel pump cartridges. Disregard any fuel found in connector during cartridge removal. It is normal that the fuel will splash into the connector during removal when aircraft is fueled. Clean canister connector with approved contact cleaner. Refer to the table below for applicable AMM references.
AMM REFERENCES Cartridge Removal Cartridge Installation LH Engine Pump AMM 28−23−02−000−801 AMM 28−23−02−400−801 RH Engine Pump AMM 28−23−02−000−801 AMM 28−23−02−400−801 APU Pump AMM 28−24−02−000−801 AMM 28−24−02−400−801 Wait a minimum of four hours, then visually inspect the canister connector cavities and wiring conduits for fuel leakage.
(d) During the four hour wait time, continuously check the canister connectors for leaks. This will provide data for the Information Feedback Sheet (Appendix 1).
NOTE: It is sometimes difficult to detect a small leak. For a quick check, place a colored paper shop towel inside the canister to help identify a leak (color of paper towel will become darker when it is wet).
(e) If there is evidence of a leak at the connector, the conduit must be purged of fuel by blowing shop air into the outlet of the conduit in the locations that follow:
(i) For APU boost pump, gain access to the conduit MPE1KD at the front spar by removing the RH landing light lens.
MODEL CL−600−2B16 Basic Issue: Oct 19/2015 Revision 03: Aug 31/2018 604−28−022 Page 5 of 11
(ii) For LH engine boost pump, gain access to the conduit MPE1QA at the front spar by removing the LH wing−to−fuselage, fwd fairing (191BB).
(iii) For RH engine boost pump, gain access to the conduit MPE2QA at the front spar by removing the RH wing−to−fuselage, fwd fairing (192BB).
(f) Once you feel that the fuel is purged, clean the connector and repeat the four hour leak check (Steps (e) and (f)).
(g) Visually inspect for any traces of fuel.
(h) If any fuel leakage reoccurs in the inspected areas, submit a Service Request for Product Support Action (SRPSA) by e−mail at:
SRPSA@aero.bombardier.com for further instructions.
(i) If no fuel leakage is detected in the inspected areas do the steps that follow:
(i) Remove the existing O−rings from the cartridges and install the new O−rings.
(ii) The aircraft can continue to operate for up to 600 flight hours or 12 months, whichever comes first from the Service Bulletin release date (Basic Issue). This inspection must be repeated every 600 flight hours or 12 months, whichever comes first.
(j) Re−install the cartridges. Refer to the table in step 1.(c) for AMM references.
(2) Inspect the wiring conduits for fuel leakage after operating the boost pumps as per the steps that follow:
(a) Operate the RHS engine electric fuel pump for 15 minutes before inspecting.
NOTE: Make sure the minimum fuel quantity in the applicable tank for boost pump operation is 500 lbs.
(b) Visually inspect for traces of fuel coming from the RHS engine boost pump at location of belly fairing screw (FS412, BL0.0). Refer to Figure 1.
NOTE: If there’s any fuel leakage from the RHS engine boost pump, clean it before you operate the LHS engine boost pump.
(c) Operate the LHS engine electric fuel pump for 15 minutes before inspecting.
(d) Visually inspect for traces of fuel coming from the LHS engine boost pump at location of belly fairing screw (FS412, BL0.0). Refer to Figure 1.
(e) Visually inspect for traces of fuel coming from the transparent wiring conduit at the APU Boost Pump conduit outlet by looking through the RHS landing light compartment glass window. Refer to Figure 2.
(i) If fuel leakage is found make sure you record this data and submit the data in an Service Request for Product Support Action (SRPSA) by e−mail at: SRPSA@aero.bombardier.com.
MODEL CL−600−2B16 Basic Issue: Oct 19/2015 Revision 03: Aug 31/2018 604−28−022 Page 6 of 11
(f) Operate the APU electric fuel pump for 15 minutes minimum before inspecting.
(g) Visually inspect for traces of fuel coming from the transparent wiring conduit at the APU Boost Pump conduit outlet by looking through the RHS landing light compartment glass window. Refer to Figure 2.
(h) If no fuel leakage is detected in the inspected areas proceed to the Close−Out.
(i) If any fuel leakage reoccurs in the inspected areas, submit a Service Request for Product Support Action (SRPSA) by e−mail at:
SRPSA@aero.bombardier.com for further instructions.
(3) Make sure you use the Appendix 1 to record the data found from the fuel leak inspections, and send it via email:
BAG_BBAD_CL600_Program@aero.bombardier.com MODEL CL−600−2B16 Basic Issue: Oct 19/2015 Revision 03: Aug 31/2018 604−28−022 Page 7 of 11
OMBARDIL CHALLENGER 604 MODEL CL-600-2B16
SCREW TO
BE REMOVED VIEW A SB604_2822_001 Location of Belly Fairing gurn Hole, FS 412.00, BL 0.0 Basic Issue: Oct 19/2015 604-28-022 I Revision 03: Aug 31/2018 Page 8 of 11
CHALLENGER 604 MBARDIE MODEL CL-600-2B16
RIGHT LANDING
LIGHTS COMPARTMENT
FUEL LEAKAGE
LOCATION MPE 1KD
APU BOOST PUMP
CONDUIT OUTLET DSB2808_001 RHS Landing Lights Compartment - APU Electrical Pump Conduit Figure 2 Basic Issue: Oct 19/2015 604-28-022 I Revision 03: Aug 31/2018 Page 9 of 11
C. Testing − Engines and/or APU Electric Fuel Pumps
(1) Test the re−installed LH and RH engine electric fuel pumps. Refer to AMM 28−23−01−710−801.
(2) Test the re−installed APU electric fuel pump. Refer to AMM 28−24−00−710−801.
D. Close−out NOTE: The steps in the Close−Out section of this Service Bulletin, except for the return−to−service tests, are recommended steps. The steps give a recommendation to install components removed during the Aircraft Set−up. This recommendation is to make sure that the aircraft is safe and ready to return to service. Alternative steps can be used at the operator discretion.
WARNING: FUEL IMBALANCE BETWEEN MAIN WING TANKS MUST BE CORRECTED AT THE END OF THIS CHECK. MOVING, TAXIING
OR TOWING THE AIRCRAFT WITH FUEL IMBALANCE EXCEEDING 400 LBS IS PROHIBITED. IF YOU DO NOT DO THIS,
YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT.
WARNING: FUEL DISTRIBUTION MUST BE RESTORED PER AFM FUEL LIMITATIONS (CHAPTER, 02-05). IF YOU DO NOT DO THIS, YOU
CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT.
(1) Redistribute the fuel or refuel tanks to correct any fuel imbalance in the tanks, per AFM fuel limitations.
(2) Install the belly fairing screw at FS412.00, BL0.0 location.
(3) Remove all tools, equipment and unwanted materials from the aircraft.
E. Recording When this Service Bulletin is completed, make an entry in the aircraft log and send the attached Incorporation Notice to Bombardier Business Aircraft Customer Services (BBACS).
In an effort to improve the quality of our technical communications, we are requesting your feedback. Please take a moment to fill out our easy on−line Service Bulletin survey:
http://csefeedback.aero.bombardier.com
3. MATERIAL INFORMATION A. Kits No kit required.
MODEL CL−600−2B16 Basic Issue: Oct 19/2015 Revision 03: Aug 31/2018 604−28−022 Page 10 of 11